Aircraft Control Surface Regulating Device Using Laser Tracker
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Solution Overview
Problem
Current methods for regulating aircraft control surfaces, particularly flaps, suffer from imprecision due to tolerance stack-up effects and require cumbersome devices that are difficult to handle, leading to increased execution time and drag issues.
Innovation Solution
A device with a structural body fixed to the aircraft's wing extrados, utilizing a dial indicator and reference ruler for precise positioning of flaps relative to the wing, eliminating the need for angle calculations and reducing weight and complexity.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Measurement precision
If traditional regulation devices using tracks as reference are used, then regulation can be performed, but measurement precision deteriorates due to tolerance stack-up effects
Solution Approach 1:
The patent introduces a laser tracker as an intermediary measurement tool that directly measures the flap position relative to the wing reference features, bypassing the traditional track-based measurement chain. This eliminates the tolerance stack-up effect because the laser tracker provides direct, high-precision measurements without relying on the cumulative tolerances of track assemblies and multiple measurement components.
Solution Approach 2:
The patent replaces the mechanical measurement system (dial indicators, physical contact with tracks) with an optical measurement system (laser tracker). The laser tracker uses laser beams to measure positions non-contactly, substituting mechanical contact and physical reference features with optical fields, thereby achieving higher precision without mechanical tolerance accumulation.
2Measurement precision
If complex regulation devices with multiple components are used, then measurement capability is improved, but device complexity increases
Solution Approach 1:
The patent extracts the essential measurement function from the complex assembly of multiple dial indicators and track components, isolating only the critical measurement points (three reference features on the wing and corresponding flap positions). The laser tracker system measures only these essential points directly, eliminating the need for intermediate mechanical linkages and multiple contact-based measurement devices.
Solution Approach 2:
The laser tracker serves multiple measurement functions simultaneously - it can measure the position of multiple flap components, verify alignment with wing reference features, and provide three-dimensional spatial relationships all with a single device. This universal measurement capability replaces the need for multiple specialized measurement tools and complex mechanical measurement assemblies.
3Manufacturing precision
If traditional measurement methods are used, then regulation can be performed, but execution time increases
Solution Approach 1:
The patent establishes a reference coordinate system and identifies reference features on the wing before performing the actual flap measurements. The laser tracker is calibrated to these pre-established references, allowing rapid subsequent measurements without requiring complex setup procedures. This preliminary establishment of measurement baselines accelerates the overall regulation process while maintaining precision.
Solution Approach 2:
The optical measurement system captures three-dimensional position data instantaneously through laser ranging, eliminating the time-consuming mechanical measurement process that required physical contact, manual reading of dial indicators, and calculation of positions based on track geometries. The laser tracker provides immediate digital measurements that can be processed and used for regulation decisions in real-time.
Data Source
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AI summary
This describes an aircraft (50) control surface (40) regulating device (10), comprising an elongated structural body (20) formed of a base (201) positioned at a first end (22) and fixed to the structure of the aircraft (50) and a regulation assembly (30) arranged at a second end (23) and positioned next to the control surfaces (40), the regulation assembly (30) comprising at least one dial indicator (31) positionable between a first measuring position (311) and a second positioning position (312) and at least one reference ruler (32) arranged adjacent to at least one dial indicator (31) and positionable between an initial position (321) and a final position (322). A method is also described for regulating aircraft control surfaces, comprising the steps of: (i) fixing a regulating device (10) on an extrados coating of the wing (50) of the aircraft, said regulating device (10) comprising a regulation assembly (30) formed of at least one dial indicator (31) and at least one reference ruler (32); (ii) measuring the dial indicator (31) in a first measuring position (311) determining a zero position of the indicator and positioning the reference ruler (32) in an initial position (321) determining a zero position of the ruler; (iii) positioning the reference ruler (32) in a final position (322) and positioning the dial indicator in a second positioning position (312) to perform the positioning of the control surface (40) regulated in relation to the wing (50) of the aircraft.